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TECHNICAL PAPERS

Unsteady Flow and Whirl-Inducing Forces in Axial-Flow Compressors: Part II—Analysis

[+] Author and Article Information
F. F. Ehrich, Z. S. Spakovszky, M. Martinez-Sanchez

Massachusetts Institute of Technology, Cambridge, MA 02139

S. J. Song

Seoul National University, Seoul, Korea

D. C. Wisler, A. F. Storace, H.-W. Shin, B. F. Beacher

GE Aircraft Engines, Cincinnati, OH 45215

J. Turbomach 123(3), 446-452 (Feb 01, 2000) (7 pages) doi:10.1115/1.1370165 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Thomas,  H. J., 1958, “Unstable Natural Vibration of Turbine Rotors Induced by the Clearance Flow in Glands and Blading,” Bull. AIM, 71, No. 11/12, pp. 1039–1063.
Alford, J., 1965, “Protecting Turbomachinery From Self-Excited Rotor Whirl,” J. Eng. Power, Oct., pp. 333–334.
Vance,  J. M., and Laudadio,  F. J., 1984, “Experimental Measurement of Alford’s Force in Axial Flow Turbomachinery,” ASME J. Eng. Gas Turbines Power, 106, No. 3, pp. 585–590.
Colding-Jorgensen,  J., 1992, “Prediction of Rotordynamic Destabilizing Forces in Axial Flow Compressors,” J. Fluids Eng., 114, No. 4, pp. 621–625.
Ehrich,  F. F., 1993, “Rotor Whirl Forces Induced by the Tip Clearance Effect in Axial Flow Compressors,” J. Vibr. Acoust., 115, pp. 509–515.
Yan, L., Hong, J., Li, Q., Zhu, Z., and Zhao, Z., 1995, “Blade Tip Destabilizing Force and Instability Analyses for Axial Rotors of Compressor,” AIAA Paper No. A95-40315, Beijing University of Aeronautics and Astronautics, Beijing, China.
Spakovszky,  Z. S., 2000, “Analysis of Aerodynamically Induced Whirling Forces in Axial Flow Compressors,” ASME J. Turbomach., 122, No. 4, pp. 761–768.
Song,  S. J., and Cho,  S. H., 2000, “Non-uniform Flow in a Compressor D Asymmetric Tip Clearance,” ASME J. Turbomach., 122, pp. 751–760.
Song,  S. J., and Martinez-Sanchez,  M., 1997, “Rotordynamic Forces Due to Turbine Rip Leakage,” ASME J. Turbomach., 119, No. 3, pp. 695–713.
Wisler,  D. C., 1985, “Loss Reduction in Axial-Flow Compressors Through Low-Speed Model Testing,” ASME J. Eng. Gas Turbines Power, 107, pp. 354–363.
Wellborn,  S. R., and Okiishi,  T. H., 1999, “Influence of Shrouded Stator Cavity Flows on Multistage Compressor Performance,” ASME J. Turbo- mach., 121, No. 3, pp. 486–498.
Martinez-Sanchez,  M., Jaroux,  B., Song,  S. J., and Yoo,  S. M., 1995, “Measurement of Tip Blade–Tip Rotordynamic Excitation Forces,” ASME J. Turbomach., 117, No. 3, pp. 384–392.

Figures

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Measured unsteady static pressure difference (pressure side−suction side) on the surface of the rotor blade at the minimum clearance condition for the maximum centerline off- set: LSRC Compressor A
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Relative contributions to the total β coefficient obtained from the experimental data for inner 50 percent and outer 50 percent spans compared to the total β coefficient: LSRC Compressor A
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Alford β coefficient for LSRC centerline offset of Compressor A. (a) Pressure integration over outer 50 percent span compared with analytic models of rotor-blade tip clearance effect. (b) Pressure integration over inner 50 percent span compared with analytic models of stator-shroud seal clearance effect.
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β coefficient for LSRC centerline offset of Compressor A with pressure integration over entire rotor span compared with analytic models of the sum of rotor-tip and stator-shroud seal clearance effects
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Compressor A performance predictions by the ISPC model compared with experimental performance data of the LSRC
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β coefficient for LSRC Compressors A, B, and C using the 2SPC method, reflecting rotor and stator tip clearance changes
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The circumferential static pressure distribution obtained from the ISPC and 2CAD models at mid-span compared to experimental data
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Computed β coefficient attributable to the compressor spool pressure effect estimated by the ISPC and 2CAD models
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β coefficient (a) and βspool coefficient (b) attributable to the compressor rotor whirl effect as estimated by the ISPC model

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